Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
  • B64D27/02—Aircraft characterised by the type or position of power plants
  • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
  • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
  • F01D1/026—Impact turbines with buckets, i.e. impulse turbines, e.g. Pelton turbines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
  • F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
  • F01D15/10—Adaptations for driving, or combinations with, electric generators
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/08—Cooling; Heating; Heat-insulation
  • F01D25/12—Cooling
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
  • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
  • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/12—Cooling of plants
  • F02C7/16—Cooling of plants characterised by cooling medium
  • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
  • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
  • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
  • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/20—Heat transfer, e.g. cooling
  • F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
  • Y02E10/00—Energy generation through renewable energy sources
  • Y02E10/70—Wind energy
  • Y02E10/72—Wind turbines with rotation axis in wind direction
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to an engine referred to as a gas- wind turbine engine.
• the present invention gas-wind turbine engine is considered to be an improvement to an engine described in United States Patent number 2,608,058 awarded to L. J. Geeraert, an improvement to an engine in United States Patent number 4,807,440 awarded to Ahmed Salem, and an improvement to an engine disclosed in United States Patent number 6,298,821 B1 awarded to Alexander Alexandrovich Bolonkin, the three prior art United States Patents indicated above does not mention a large fan air flow or usable air flow from a fan housing assembly and the fan assembly for cooling the turbine rotor blades so the above mentioned prior art engines when manufactured without proper cooling the rotor blades may result to an engine failure in a long period of engine operation.
• the present invention gas-wind turbine engine further is an improvement to the prior art jet turbine engine because the prior art jet turbine engine does not utilize air or wind directly from a fan for cooling the turbine rotor and for cooling the turbine rotor blades of the prior art engine.
• the prior art engines further was not disclosed having a wind or usable air flow or large fan air flow from a fan for giving additional push for rotation to the turbine rotor which gives more force to rotate the engine turbine rotor shaft.
• the prior art gas turbine engines does not include a wind turbine but in one the present invention engine configuration includes a wind turbine assembly.
• the prior art turbine engine for: jet propelled aircraft, flying machine with turbine engine, land vehicle, water vehicle, amphibious vehicle, power shaft turbine, jetpack, auxiliary power unit, and engine for other electric generating systems are a lot more complicated or has more moving parts and therefore the prior art engine cost a lot more and bound to have more problems related to the numerous moving parts and the prior art turbine engine additionally is somewhat problematic since the rotor blades are exposed constantly to hot exhaust gases during operation of the prior art turbine engine which requires a complicated and energy wasting cooling system, requires expensive materials, and requires frequent maintenance of said prior art turbine engine which likely increase the prior art turbine engine maintenance cost.
• the exhaust gas flow which pushes the blades of a gas-wind turbine engine rotor eventually be at the mixture flow duct.
• the present invention gas-wind turbine engine in other configuration includes an optional wind turbine assembly having a wind turbine rotor, said wind turbine rotor attached to the gas-wind turbine engine main shaft, said wind turbine is housed by the engine housing system and said wind turbine is rotated by exhaust gases and additionally rotated by the air flow from the fan and the fan housing assembly, the exhaust gas flow and the air flow going to the wind turbine are directed by the fourth guide vanes.
• Some of the fourth guide vanes maybe attached to the second wall of a gas-wind turbine engine housing so that the air flow for cooling would not be substantially altered by the exhaust gas flow.
• the pressure of the mixture of air and exhaust gas at the mixture flow duct could be reduced by making the mixture flow duct larger and also could be done by making the external housing smaller or making the large fan air flow duct smaller to increase the air pressure going into the gas-wind turbine engine rotor housing.
• the present invention gas-wind turbine engine having either an air cooling system or having both an air cooling system and a liquid cooling system, said air cooling system is adapted for aviation purposes or adapted for other gas-wind turbine engine model since the gas-wind turbine engine with air cooling system likely be an engine with less weight but an air cooled and a liquid cooled gas-wind turbine engine likely adapted for power generating station or when the gas-wind turbine engine has to run in a relatively hot environment or when the liquid medium for cooling the gas-wind turbine engine is needed for heating purposes which likely a requirement in a land operating gas-wind turbine engine system or an amphibious vehicle with a gas-wind turbine engine system or a body of water operating vehicle with a gas-wind turbine engine system.
• the gas-wind turbine engine is a simple rotary engine having a starting system which rotates the gas-wind turbine engine main shaft and activates the air compressing system and also rotates the gas-wind turbine engine fan, the air compressing system which includes a compressor fan is designed to deliver more air to the combustor, the compressed air goes along air duct or through other suitable means, the air compressing system supplies air for cooling the combustor and supplies air for the combustion of fuel and air mixture in the combustor, and when the fuel and air mixture is ignited the gas pressure in the combustor increases and the pressure at the exhaust gas duct also increases which also increases the pressure at the area where the gas- wind turbine engine rotor is located so that the gas pressure pushes the gas- wind turbine engine rotor blades and rotates the gas-wind turbine engine rotor and also rotates the gas-wind turbine engine main shaft which creates torque for the present invention engine, the rotation of the gas-wind turbine engine main shaft also rotates the gas-wind turbine engine fan so that the fan generates an air pressure for
• the gas- wind turbine engine may just have a single shaft or several shaft which is referred to as a power shaft means but in the present invention specification refers to a gas-wind turbine engine main shaft since said gas-wind turbine engine main shaft is attached to the gas-wind turbine engine rotor, the specification refers to engine fan shaft since the engine fan shaft is attached to an engine fan and the specification refers to a large fan shaft because it is attached to the large fan although the gas- wind turbine engine in the present invention may just have a single shaft.
• the air compressing system as shown in the present invention could be substituted with another air compressing system. Changing the air compressing system or changing other features of the present invention engine does not invalidate the claims of the present invention.
• Gas-wind turbine engine 1.00, First rotation axis— 1.10, First plane— 1.11, Second plane— 1.12, Fourth plane-- 1.14, Fifth plane— 1.15, Sixth plane— 1.16, Engine first housing— 1.17, Engine second housing— 1.18, Engine third housing— 1.19, Usable air flow— 1.20, Air passages— 1.21, Air pipe assemblies— 1.25, Air hose assemblies— 1.27, Air convergence zone— 1.29, Shaft play sensor— 1.30, First part— 1.31 , Second part— 1.32, Turbo air space— 1.40, First space— 1.41, Second space— 1.42, Third space— 1.43, Air gap— 1.44, Belt— 1.52, Bracket— 1.54, Radial arc— 1.70, Insert— 1.80, Gear— 1.90, External housing— 2.00, Engine fan housing— 2.11, Engine fan— 2.12, Engine fan shroud— 2.13, Engine fan shaft— 2.14, Engine fan hub— 2.15, Engine fan blades— 2.18, Air pressure sensor— 2.19, Core shell— 2.20, Fourth guide vane
• Combustion chamber 4.11 , Swirl vanes— 4.12, Liner— 4.13, Corrugated joint— 4.15, Small through spaces— 4.16, Combustor seal— 4.17, Exhaust gas duct— 4.20, Exhaust gas duct housing—
• Figure 1 illustrates the first end view of the gas-wind turbine engine having an air cooled system and adapted to generate thrust.
• Figure 2 illustrates the side elevation view of the gas-wind turbine engine shown in Figure 1.
• Figure 3 illustrates the section 1 -1 ' of the gas-wind turbine engine shown in Figure 1 and showing an internal air compressing system.
• Figure 4 shows the section 2-2’ of Figure 2.
• Figure 5 illustrates an alternate section 2-2’ of the gas-wind turbine engine shown in Figure 2.
• Figure 6 illustrates the first end 666 view of the gas-wind turbine engine designed to generate torque and having an air cooling system and having an external air compressing system.
• Figure 7 illustrates the second end 888 view of the gas- wind turbine engine shown in Figure 8 and second end view of the gas-wind turbine engine shown in Figure 6.
• Figure 8 illustrates the third location 999 view of the gas-wind turbine engine shown in Figure 6.
• Figure 9 illustrates section 4-4’of the gas-wind turbine engine shown in Figure 8.
• Figure 10 illustrates section 3-3’ in Figure 6.
• Figure 1 1 illustrates the first end view of another gas-wind turbine engine designed to generate torque and having an external air compressing system and a liquid cooled system supplemented by an air cooling system.
• Figure 12 illustrates the second end 888 view of the gas-wind turbine engine shown in Figure 13 and second end view the gas-wind turbine engine shown Figure 11.
• Figure 13 illustrates third location 999 view of the gas-wind turbine engine shown in Figure 11.
• Figure 14 illustrates section 6-6’ of Figure 13.
• Figure 15 illustrates section 5-5’of the gas- wind turbine engine shown in Figure 11.
• Figure 16 illustrates the first end 666 view of a gas-wind turbine engine having an external air compressing system and having an air cooled system designed to generate torque.
• Figure 17 illustrates the second end 888 view of the gas- wind turbine engine in Figure 18 and second end view of the gas-wind turbine engine shown Figure 16.
• Figure 18 illustrates the third location 999 view of the gas-wind turbine engine shown in Figure 16.
• Figure 19 illustrates section 8-8’ of Figure 18.
• Figure 20 shows section 7-7’ of Figure 16.
• Figure 21 illustrates the gas-wind turbine engine with an air cooled system having a typical belt arrangement wherein the booster air compressor is driven by second electric motor.
• Figure 22 illustrates the gas-wind turbine engine with an air cooled system having a typical belt arrangement showing the booster air compressor is driven by second electric motor and wherein the auxiliary air compressor driven by a first electric motor.
• Figure 23 illustrates the gas-wind turbine engine with an air cooled system and liquid cooled system having a typical belt arrangement wherein the booster air compressor is driven by a second electric motor.
• Figure 24 illustrates the gas-wind turbine engine with an air cooled system and liquid cooled system having a typical belt arrangement and showing the booster air compressor is driven by a second electric motor and wherein the auxiliary air compressor is driven by a first electric motor.
• Figure 25 shows section 9-9’ in Figure 6 of a typical auxiliary air compressor.
• Figure 26 illustrates the section 10-10’ in Figure 6 of a typical booster air compressor.
• Figure 27 illustrates an enlarged drawing for clarity of a typical gas pressure ring for present invention engine designed to generate torque.
• Figure 28 illustrates an enlarged drawing as seen on first location 111 view in Figure 27 for clarity of a typical gas pressure ring and typical gas pressure ring spring for present invention engine designed to generate torque where the gas-wind turbine engine rotor hub is not shown to show more details of the gas pressure ring and gas pressure ring spring.
• Figure 29 shows a sketch of a first guide vane, walls, housing gaps, fourth guide vanes, and gas-wind turbine engine rotor of the present invention gas-wind turbine engine.
• Figure 30 illustrates an enlarged drawing for clarity of a typical oil ring of the present invention engine designed to generate torque.
• Figure 31 illustrates an enlarged drawing as seen on second location 222 view in Figure 30 for clarity of a typical oil ring and typical oil ring spring of the present invention engine designed to generate torque where the gas-wind turbine engine rotor hub is not shown to show more details of the oil ring and oil ring spring.
• Figure 32 shows a known bearing retainer with tab lock.
• Figure 33 shows a sketch of the exhaust duct housing attached to the third wall of the gas-wind turbine engine rotor housing and the gas-wind turbine engine rotor housing composed of an engine first housing having a first wall, an engine second housing having a second wall, and an engine third housing having a third wall.
• Figure 34 shows a sketch of the exhaust duct housing attached to the third wall of the gas- wind turbine engine rotor housing and first part of a gas-wind turbine engine rotor housing includes a first wall and a third wall and the second part of a gas-wind turbine engine rotor housing includes a second wall.
• Figure 35 shows a sketch of the exhaust duct housing attached to the first wall of the gas-wind turbine engine rotor housing and the first part of a gas-wind turbine engine rotor housing having a first wall and having a third wall while portion of gas-wind turbine engine rotor housing includes a second wall.
• Figure 36 shows a sketch of the exhaust duct housing attached to the second wall of the gas- wind turbine engine rotor housing and the first part of a gas-wind turbine engine rotor housing having a first wall and the second part of a gas-wind turbine engine rotor housing having a second wall and having a third wall.
• Figure 37 shows a sketch of the exhaust duct housing attached to the third wall of the gas-wind engine rotor housing and attached to the second wall of the gas-wind turbine engine rotor housing and the first part of a gas-wind turbine engine rotor housing having a first wall and the second part of a gas-wind turbine engine rotor housing having a second wall and having a third wall.
• Figure 38 shows a sketch of the exhaust duct housing is attached to the first wall of the gas-wind turbine engine rotor housing and attached to the third wall of the gas-wind turbine engine rotor housing and first part of a gas-wind turbine engine rotor housing having a first wall and a having a third wall while the second part having a second wall.
• Figure 39 shows a view of the gas-wind turbine engine rotor.
• Figure 40 shows a section as seen along line l-G in Figure 39 of a gas-wind turbine engine rotor blade when cut by a radial arc.
• Figure 41 shows an illustration of a first guide vane.
• Figure 42 shows the section of a first guide vane along line 2-2’ in Figure 41 when cut by a radial arc.
• Figure 43 shows a wind turbine rotor blade cut by a radial arc.
• Figure 44 shows the section along line 3-3’ in Figure 43 of the wind turbine rotor blade cut by the radial arc.
• Figure 45 shows another present invention configuration of a bearing means assembly with a cylindrical roller bearing, insert, and tapered roller bearings which could be used for the present invention gas-wind turbine engine.
• Figure 46 shows another present invention configuration of a bearing means assembly with ball bearings, insert, and a cylindrical roller bearing which could be used for the present invention gas-wind turbine engine.
• Figure 47 shows the transmission and a second cooling fan in an air cooled gas-wind turbine engine.
• Figure 48 shows the gas-wind turbine engine having both an air cooled and liquid cooled which includes a transmission and a second cooling fan.
• Figure 49 is a schematic diagram of the present invention typical compressed air flow with internal air compressing system.
• Figure 50 is a schematic diagram of another present invention typical compressed air flow in an internal air compressing system similar to a jet engine.
• Figure 51 is a schematic diagram of the present invention typical oil flow.
• Figure 52 is a schematic diagram of the present invention typical fuel flow.
• Figure 53 is a schematic diagram of another present invention typical compressed air flow of an external air compression system.
• Figure 54 is a schematic diagram of the present invention typical compressed air flow having an auxiliary air compressor and a booster air compressor.
• Figure 55 is a schematic diagram of the present invention typical liquid cooling flow.
• Figure 56 shows a schematic diagram of an air bleeding system from an auxiliary air compressor or an internal air compressing system to the air passages at the second wall of the gas-wind turbine engine rotor housing.
• Figure 57 shows a schematic diagram of an air bleeding system from a booster air compressor to the air passages at the second wall of the gas-wind turbine engine rotor housing.
• Figure 58 shows an illustration of a fourth guide vane.
• Figure 59 shows the section of a fourth guide vane along line 4-4' in Figure 58 when cut by a radial arc.
• Figure 60 shows a detailed and enlarged sketch of the expansion gap of the present invention exhaust gas pressure ring.
• Figure 61 shows a detailed and enlarged sketch of the expansion gap of the present invention oil ring.
• Figure 62 shows an illustration or sketch of an optional oil duct located adjacent to the gas- wind turbine engine main shaft at the gas-wind turbine engine rotor hub which is non-parallel to the rotation axis of the gas-wind turbine engine rotor shaft so that the oil circulates for more efficient cooling of the gas-wind turbine engine rotor.
• Figure 63 shows an illustration or sketch of an alternate coil spring for the oil rings.
• Figure 64 shows is a schematic diagram of the present invention engine having three main housing which includes: first housing with a first wall, second housing with a second wall, and third housing with a third wall in an air cooled present invention engine and showing the bearing used are ball bearings.
• Figure 65 is a schematic diagram of the present invention engine having three main housing which includes: engine first housing with a first wall, and engine second housing having a second wall, and third housing having a third wail in a liquid cooled present invention engine and showing the bearings used are tapered roller bearings.
• a gas-wind turbine engine 1.00 having an air cooling system said gas-wind turbine engine 1.00 comprising: an engine housing system, an air pressure sensor 2.19, a shaft play sensor 1.30, structural guide vanes 5.90, a large fan assembly having a large fan 5.00, an internal air compressing system 3.00 or a plurality of internal air compressing system 3.00, at least one combustor 4.00 having a combustor housing 4.10, at least one compressed air delivery system, at least one compressed air receiving means 3.50, at least one fuel system, an electrical system having at least one fuel and air mixture ignition system with at least one fuel and air mixture ignition means 4.50, at least one exhaust gas duct housing 4.25, at least one gas-wind turbine engine rotor assembly, a lubricating system, a power shaft means, gas-wind turbine engine accessories, a plurality of bearing means assembly 9.00, a plurality of known exhaust gas pressure sealing means, a plurality of known oil sealing means, fins 5.50, gears 1.90, a large fan cone 5.07, fast
• the engine housing system is either adapted for a high bypass air flow engine configuration or adapted for a low bypass air flow engine configuration
• said engine housing system includes: an external housing 2.00, an engine cowling 2.70, a core shell 2.20, a turbo air space 1.40, at least one air gap 1.44, a second space 1.42, a third space 1.43, at least one gas-wind turbine engine rotor housing 2.30, a plurality of bearing means assembly housing 9.70, fourth guide vanes 2.40, and a mixture flow duct 9.20, in other configuration of the present invention some of the said bearing means assembly housing 9.70 is incorporated with said gas-wind turbine engine rotor housing 2.30, said external housing 2.00 includes a large fan housing assembly and a main frame 5.30, said main frame 5.30 includes a pylon 5.80 and a large fan air flow duct 9.50, the large fan assembly which is complimented by the large fan housing assembly generates a large fan air flow 5.20 during the operation of said gas- wind turbine engine 1.00, said large fan air flow 5.
• bearing means assembly 9.00 includes bearings 9.10 and bearing means assembly accessories, said bearing means assembly 9.00 prevents too much axial movement and prevents too much radial movement of a shaft in relation to the bearing means assembly housing 9.70, said bearings 9.10 could be in the form of ball bearings 9.15, tapered roller bearings 9.16, cylindrical roller bearings 9.17, journal bearings 9.60, and other suitable form of bearings 9.10, in one configuration of the present invention
• said bearing means assembly accessories includes: spacers 9.11, keys 5.60, inserts 1.80, O-rings 5.65, bearing retainers 5.55, tab lock 5.56, and oil seals 6.82, said bearing retainers 5.55 and said bearing means assembly housing 9.70 maintains said bearings 9.10 position, said bearing retainer 5.55 could be a known system which prevents said bearings from moving out of place, said bearing retainer 5.55 could be in the form of tabbed and threaded fasteners, said bearing retainer 5.55 works with the compliment of a tab lock 5.56, said spacers 9.11 are designed to transfer
• the large fan housing assembly includes: a large fan housing 5.02, a large fan shroud 5.03, and turbo guide vanes 4.90
• said turbo guide vanes 4.90 in one of the present invention configuration includes oil duct 7.30 for entry of feed oil and exit of return oil for the bearing means assembly 9.00, at least one of said bearing means assembly 9.00 located adjacent to the large fan assembly, said oil duct 7.30 of said large fan housing 5.02 are oil spaces along said turbo guide vanes 4.90, said oil duct 7.30, the oil line assemblies 6.70, and the oil hose assemblies 6.95 carries the oil to and from said bearing means assembly 9.00 at said large fan housing 5.02, said oil duct 7.30, said oil hose assemblies 6.95, and said oil line assemblies 6.70 communicates with the lubricating system; wherein the large fan assembly and the large fan assembly during operation of the gas-wind turbine engine 1.00 generates a large fan air flow 5.20 for thrust and for cooling said gas- wind turbine engine 1.00, said large fan air flow 5.20 cools the following: combustor housing 4.
• the lubricating system having communicating means with the plurality of bearing means assembly 9.00, said lubricating system supplies oil for cooling and lubrication of said plurality of bearing means assembly 9.00, said lubricating system includes at least one oil pump assembly 7.00, oil line assemblies 6.70, oil hose assemblies 6.95, and lubricating system accessories, said lubricating system accessories includes an oil cooler and oil containment unit 8.50, the parts that supports the bearing means assembly housing 9.70 of a large fan housing 5.02 includes the turbo guide vanes 4.90, said turbo guide vanes 4.90 could serve as an oil cooler;
• the internal air compressing 3.00 system includes: an internal air compressing system fan 3.10, an internal air compressing system fan housing 3.20, an internal air compressing system fan shroud 3.22, an internal air compressing system shaft 3.21, internal air compressing system first stationary vanes assembly 3.23, internal air compressing system second stationary vanes assembly 3.24, compressed air space 6.90, air duct 5.15, and internal air compressing system air compressing system shaft mounted vanes assembly 3.25
• said internal air compressing system fan 3.10 includes an internal air compressing system fan hub 3.11 and internal air compressing system fan blades 3.12
• said internal air compressing system 3.00 supplies compressed air to one or more of the following: to a combustor 4.00 for combustion of fuel and air mixture, to a combustor housing 4.10 for cooling purposes, and to the gas-wind turbine engine 1.00 for additional cooling of hot parts of said gas-wind turbine engine 1.00, said air compressing system as known having either an axial air compressing system or centrifugal air compressing system or having both an axial air compressing
• the combustor 4.00 is designed to generate exhaust gas flow 4.70 during a gas-wind turbine engine 1.00 operation, said exhaust gas flow 4.70 is a result when fuel and air mixture is ignited
• said combustor 4.00 includes one or more of the following: combustor housing 4.10, a combustion chamber 4.11, swirl vanes 4.12, a liner 4.13, and a combustor seal 4.17, said liner 4.13 and said combustor seal 4.17 is a known aviation system which could be adapted for said gas-wind turbine engine 1.00, said exhaust gas flow 4.70 goes through the exhaust gas duct housing 4.25 along the exhaust gas duct 4.20, said combustor housing 4.10 could either be cooled by one or more of the following: compressed air cooling, large fan air flow cooling, or other air flow cooling, said combustor 4.00 having communicating means with: a fuel delivery means 4.30, one or more fuel and air mixture ignition means 4.50, and an air compressing system, said combustor housing 4.10 in one of the present invention configuration includes
• said main frame 5.30 allows access to said combustor 4.00 for parts replacement, said combustor housing 4.10 includes fins 5.50 to radiate heat and includes an starting air tube 3.55, said starting air tube 3.55 having communicating means with other source of compressed air;
• gas-wind turbine engine rotor assembly includes a gas-wind turbine engine rotor
• said gas- wind turbine engine rotor 6.10 includes a gas-wind turbine engine rotor hub 6.20, said gas-wind turbine engine rotor hub 6.20 having a plurality of gas-wind turbine engine rotor blades 6.60, said plurality of gas-wind turbine engine rotor blades 6.60 are attached to said gas-wind turbine engine rotor hub 6.20, said gas-wind turbine engine rotor blades 6.60 may just be some extensions with different configuration from said gas-wind turbine engine rotor hub 6.20, said gas-wind turbine engine rotor blades 6.60 could be of any other suitable known shape, said gas-wind turbine engine rotor blades 6.60 could be made of different material as compared to the gas-wind turbine engine rotor hub 6.20 or said gas-wind turbine engine rotor blades 6.60 could be made of same material as said gas-wind turbine engine rotor hub 6.20, said gas-wind turbine engine rotor blades 6.60 extends in an outwardly manner from said gas-
• the power shaft means is a system in which the large fan shaft 5.04, the internal air compressing system shaft 3.21, and the gas- wind turbine engine main shaft 6.50 is a single continuous shaft or the large fan shaft 5.04, the internal air compressing system shaft 3.21, and the gas-wind turbine engine main shaft 6.50 are separate shafts where said large fan shaft 5.04, said internal air compressing system shaft 3.21, and said gas- wind turbine engine main shaft 6.50 communicates with one another;
• mixture flow duct 9.20 directs the mixture of a portion of large fan air flow 5.20 and exhaust gas flow 4.70 for thrust;
• bearing means assembly housing 9.70 supports one bearing 9.10 or supports a plurality of bearings 9.10
• said bearing means assembly housing 9.70 in one present invention configuration includes a housing oil bypass 5.40, said housing oil bypass 5.40 allows proper circulation of oil at the bearing means assembly housing 9.70, said bearing means assembly housing 9.70 and said bearings 9.10 in another present invention configuration includes a matching groove for a key 5.60, said key 5.60 prevents said bearings 9.10 from damaging said bearing means assembly housing 9.70;
• the gas-wind turbine engine rotor housing 2.30 is adapted to allow installation of required parts of the gas-wind turbine engine 1.00 into said gas-wind turbine engine rotor housing 2.30 which includes allowing the installation of a gas-wind turbine engine rotor assembly, said gas-wind turbine engine rotor housing 2.30 allows the gas-wind turbine engine main shaft 6.50 and the gas-wind turbine engine rotor 6.10 to rotate, said gas-wind turbine engine rotor housing 2.30 having walls 2.41, at least two housing gaps 2.42, at least one exhaust gas duct opening 2.43, fins 5.50, and gas-wind turbine engine rotor assembly space, said walls 2.41 includes a first wall 2.44, a second wall 2.45, and a third wall 2.46, said first wall 2.44, said second wall 2.45, and said third wall 2.46 could be made of different sections and assembled together, in one configuration of the present invention said housing gap 2.42 at said second wall 2.45 being wider than said housing gap 2.42 at said first wall 2.44 are designed so that the exhaust gas flow 4.70 moves out from
• a gas-wind turbine engine 1.00 according to the first disclosure wherein parts adjacent to: the gas-wind turbine engine main shaft 6.50, the large fan shaft 5.04, and the internal air compressing system shaft 3.21 having a communicating means with the shaft play sensor 1.30, said shaft play sensor 1.30 monitors excessive play of: said gas-wind turbine engine main shaft 6.50, said large fan shaft 5.04, and said internal air compressing system shaft 3.21 to warn crew of impending failure so it could be shut down before extensive damage is done.
• a gas-wind turbine engine 1.00 having an air cooling system or having both an air cooling system and a liquid cooling system, said air cooling system includes fins 5.50, air pipe assemblies 1.25, and air passages 1.21, said liquid cooling system includes: a heat radiator 2.90, a liquid cooling pump 2.92, liquid cooling passageways 2.93, liquid cooling medium, liquid cooling spaces 2.94, and liquid cooling accessories, said liquid cooling accessories includes coolant hose assemblies 2.91 and coolant pipe assemblies 2.95, said coolant hose assemblies 2.91 and said coolant pipe assemblies 2.95 are interchangeable, said gas-wind turbine engine 1.00 comprising: an engine housing system, an air pressure sensor 2.19, an engine fan assembly having an engine fan 2.12 and engine fan shaft 2.14, an air filtering system 3.71 or a plurality of air filtering system 3,71, an air compressing system or a plurality of air compressing system, at least one combustor 4.00, at least one compressed air delivery means, at least one compressed air receiving means 3.50, a fuel system, an electrical system having a fuel and air mixture ignition system
• said low bypass air flow engine configuration includes zero bypass air flow engine configuration
• said engine housing system includes: an engine fan housing assembly, a core shell 2.20, first guide vanes 2.50, at least one gas-wind turbine engine rotor housing 2.30, fourth guide vanes 2.40, a plurality of bearing means assembly housing 9.70, a mixture flow duct 9.20, exhaust gas manifold 9.25, and fastening system with fasteners 9.30, said engine housing system consist of a first part 1.31 and a second part 1.32 or consist of an engine first housing 1.17, an engine second housing 1.18, and an engine third housing 1.19, said engine fan housing assembly includes an engine fan housing 2.11 and an engine fan shroud 2.13, said engine fan shroud 2.13 attached to said engine fan housing 2.11, said bearing means assembly housing 9.70 includes a housing oil bypass 5.40, said engine fan assembly includes an engine fan 2.12, said engine fan 2.12 having engine fan hub 2.15 and engine fan blades 2.18, said gas-wind turbine engine rotor housing 2.30 allows the installation of said gas- wind
• a gas-wind turbine engine 1.00 having an air cooling system or having both an air cooling system and a liquid cooling system, said air cooling system includes fins 5.50, air pipe assemblies 1.25, and air passages 1.21, said liquid cooling system includes: a heat radiator 2.90, a liquid cooling pump 2.92, liquid cooling passageways 2.93, liquid cooling medium, liquid cooling spaces 2.94, and liquid cooling accessories, said liquid cooling accessories includes coolant hose assemblies 2.91 and coolant pipe assemblies 2.95, said gas-wind turbine engine 1.00 comprising: an engine housing system, an air pressure sensor 2.19, an engine fan assembly having an engine fan 2.12, an air filtering system 3.71 or a plurality of air filtering system 3.71, an air compressing system or a plurality of air compressing system, at least one combustor 4.00, at least one compressed air delivery means, at least one compressed air receiving means 3.50, a fuel system, an electrical system having a fuel and air mixture ignition system with at least one fuel and air mixture ignition means 4.50, at least one exhaust gas duct housing 4.25 having an exhaust
• the engine housing system is adapted for a low bypass air flow engine configuration, said low bypass air flow engine configuration includes zero bypass air flow engine configuration, said engine housing system consist either a first part 1.31 and a second part 1.32 or an engine first housing 1.17, an engine second housing 1.18, and an engine third housing 1.19, said engine housing system includes: an engine fan housing assembly, a core shell 2.20, first guide vanes 2.50, at least one gas-wind turbine engine rotor housing 2.30, a plurality of bearing means assembly housing 9.70, fourth guide vanes 2.40, a gas-wind turbine engine supporting means, a mixture flow duct 9.20, and exhaust gas manifold 9.25, in other configuration of the present invention some of said bearing means assembly housing 9.70 is incorporated with said gas-wind turbine engine rotor housing 2.30, during the operation of a gas-wind turbine engine said engine fan housing assembly and the engine fan assembly generates an usable air flow 1.20 for air cooling hot parts of said gas-wind turbine engine 1.00 and for additional torque for said gas-wind turbine engine 1.00,
• the engine fan assembly having an engine fan 2.12, said engine fan 2.12 includes an engine fan hub 2.15 and an engine fan shaft 2.14, said engine fan hub 2.15 includes a plurality of engine fan blades 2.18, said plurality of engine fan blades 2.18 attached to said engine fan hub 2.15, said engine fan hub 2.15 attached to said engine fan shaft 2.14, during operation and during idle times of said gas-wind turbine engine 1.00 the first guide vanes 2.50, the bearing means assembly housing 9.70, and the bearing means assembly 9.00 maintain rotational stability of the engine fan shaft 2.14 while the first guide vanes 2.50, the fourth guide vanes 2.40, the bearing means assembly housing 9.70 and the bearing means assembly 9.00 maintains rotational stability of the gas-wind turbine engine main shaft 6.50, said first guide vanes 2.50 and said fourth guide vanes 2.40 could each be configured to include an oil duct 7.30 for said bearing means assembly 9.00, said oil duct 7.30 which includes return oil duct and feed oil duct are oil spaces along said first guide vanes 2.50, oil spaces along said fourth guide vanes
• said oil duct 7.30 are complimented by the oil line assemblies 6.70 and the oil hose assemblies 6.95 which carries the oil to and from said bearing means assembly 9.00, said oil line assemblies 6.70 and said oil hose assemblies 6.95 are interchangeable, said oil duct 7.30, said oil line assemblies 6.70, and said oil hose assemblies 6.95 communicates with the lubricating system;
• the combustor 4.00 is designed to generate exhaust gas flow 4.70 during a gas-wind turbine engine 1.00 operation, said exhaust gas flow 4.70 is known as a result of the movement of gases when fuel and air mixture is ignited, said combustor 4.00 includes: a combustor housing 4.10, a combustion chamber 4.11, swirl vanes 4.12, and in other configuration of said combustor 4.00 includes a liner 4.13 and a combustor seal 4.17, said liner 4.13 and said combustor seal 4.17 are known aviation related system adapted for the gas-wind turbine engine 1.00, said exhaust gas flow 4.70 goes through the exhaust gas duct 4.20, said combustor housing 4.10 includes an air duct 5.15, said combustor housing 4.10 could either be cooled by one or more of the following: liquid cooling, compressed air cooling, usable air flow 1.20 cooling or other air flow cooling, said combustor 4.00 having communicating means with: a fuel delivery means 4.30, one or more fuel and air mixture ignition means 4.50, and
• the air compressing system is either an internal compressing system or an external air compressing system or having both an external air compressing system and internal compressing system
• said internal compressing system is a known air compressing system
• said external compressing system comes in other form which includes the present invention auxiliary air compressing system
• said auxiliary air compressing system includes an optional booster air compressing system, said air compressing system having a known air bleeding system, the compressed air delivery means to a combustor 4.00 from an external air compressing system uses one or more of: air pipe assembly 1.25 and air hose assemblies 1.27 or with other suitable means;
• the gas-wind turbine engine rotor assembly includes a gas-wind turbine engine rotor 6.10 and a gas-wind turbine engine main shaft 6.50, said a gas-wind turbine engine rotor 6.10 having a gas-wind turbine engine rotor hub 6.20, said gas-wind turbine engine rotor hub 6.20 includes a plurality of gas-wind turbine engine rotor blades 6.60, a plurality of exhaust gas pressure ring hub groove 6.40, and a plurality of oil ring hub groove 6.26, said exhaust gas pressure ring hub groove 6.40 having an exhaust gas pressure ring hub groove inner periphery 6.45, said oil ring hub groove 6.26 having oil ring hub groove inner periphery 6.29, said exhaust gas pressure ring hub groove 6.40 is adapted for an exhaust gas pressure sealing means while said oil ring hub groove 6.26 is adapted for an oil sealing means, said plurality of gas-wind turbine engine rotor blades 6.60 are attached to said gas-wind turbine engine rotor hub 6.20, said gas-wind turbine engine rotor hub 6.
• the gas-wind turbine engine rotor housing 2.30 allows installation of required parts of the gas-wind turbine engine 1.00 into said gas-wind turbine engine rotor housing 2.30, said required parts includes the gas-wind turbine engine rotor assembly, said gas-wind turbine engine rotor housing 2.30 allows the gas-wind turbine engine main shaft 6.50 and the gas-wind turbine engine rotor 6.10 to rotate, said gas-wind turbine engine rotor housing 2.30 having walls 2.41, at least two housing gaps 2.42, at least one exhaust gas duct opening 2.43, and gas-wind turbine engine rotor assembly space, said gas- wind turbine engine rotor assembly space includes a second space 1.42, said second space 1.42 specifically allows said gas-wind turbine engine rotor 6.10 to rotate, the exhaust gas duct housing 4.25 is attached to said gas-wind turbine engine rotor housing 2.30 so that said exhaust gas flow 4.70 be allowed to move in to a part of said second space 1.42 at said gas-wind turbine engine rotor housing 2.30, said walls 2.41 includes a first wall 2.44,
• the usable air flow 1.20 in motion pushes the gas-wind turbine engine rotor blades 6.60 and rotates the gas- wind turbine engine rotor 6.10 on the first rotation axis 1.10 of a gas- wind turbine engine main shaft 6.50 which adds torque to the gas-wind turbine engine 1.00, said usable air flow 1.20 also maintains an acceptable operating temperature of said gas-wind turbine engine rotor 6.10 and additionally helps maintain an acceptable operating temperature of said gas-wind turbine engine 1.00;
• the lubricating system having communicating means with a bearing means assembly 9.00, said lubricating system supplies oil for cooling and lubrication of the plurality of bearing means assembly 9.00, said lubricating system having communicating means with said bearing means assembly 9.00 of an external air compressing system, said lubricating system includes at least one oil pump assembly 7.00 and lubricating system accessories, said lubricating system accessories includes oil containment unit 8.50, oil line assemblies 6.70, and includes an oil cooler, the first guide vanes 2.50 could be used as an oil cooler,
• bearing means assembly 9.00 is supported by the bearing means assembly housing 9.70
• said bearing means assembly includes bearings 9.10 and bearing means assembly accessories
• said bearings 9.10 could be in the form of ball bearings 9.15, tapered roller bearings 9.16, cylindrical roller bearings 9.17, journal bearings 9.60, and other suitable form of bearings 9.10
• said bearing means assembly 9.00 prevents too much axial movement and prevents too much radial movement of a shaft in relation to the bearing means assembly housing 9.70
• said bearing means assembly accessories includes: spacers 9.11, inserts 1.80, keys 5.60, O-ring 5.65, bearing retainers 5.55, and oil seals 6.82
• said bearing retainer 5.55 and said bearing means assembly housing 9.70 maintains the proper bearing 9.10 position
• said bearing retainer 5.55 could be a known system which prevents said bearings from moving out of place
• said bearing retainer 5.55 could be in the form of tabbed and threaded fasteners
• said bearing retainer 5.55 works with the compliment of a tab lock 5.56
• the bearing means assembly housing 9.70 supports one bearing 9.10 or supports a plurality of bearings 9.10
• said bearing means assembly housing 9.70 in one present invention configuration includes a housing oil bypass 5.40, said housing oil bypass 5.40 is a groove along said bearing means assembly housing 9 70, said housing oil bypass 5.40 allows proper circulation of oil at the bearing means assembly housing 9.70, said bearing means assembly housing 9.70 and said bearings 9.10 in another present invention configuration includes a matching groove for a key 5.60, said key 5.60 prevents said bearings 9.10 from damaging said bearing means assembly housing 9.70;
• a power shaft means is a system in which the engine fan shaft 2.14 and a gas-wind turbine engine main shaft 6.50 is a single continuous shaft or in other present invention configuration said engine fan shaft 2.14 and said gas-wind turbine engine main shaft 6.50 are separate shafts but said engine fan shaft 2.14 and said gas-wind turbine engine main shaft 6.50 communicates with one another;
• liquid cooling system is a known engine configuration
• said liquid cooling system accessories includes an electrically operated fan or gas-wind turbine engine shaft mounted fan, liquid cooling passageways 2.93, coolant hose assemblies 2.91, coolant pipe assemblies 2.95, and liquid cooling spaces 2.94
• said liquid cooling passageways 2.93 and liquid cooling spaces 2.94 are located at the following: the walls 2.41 of the gas-wind turbine engine rotor housing 2.30, the combustor housing 4.10, and the exhaust gas duct housing 4.25, said liquid cooling passageways 2.93, said coolant hoses assemblies 2.91, coolant pipe assemblies 2.95, and said liquid cooling spaces 2.94 communicates with said liquid cooling pump 2.92, said coolant hoses assemblies 2.91 and coolant pipe assemblies 2.95 are interchangeable, said liquid cooling passageways 2.93 and said liquid cooling spaces 2.94 are used for cooling other parts of the gas-wind turbine engine 1.00 with a liquid cooling system, said liquid cooling passageways 2.93 and said liquid cooling spaces 2.94 are designed so that liquid cooling medium could flow in and flow out, said liquid cooling medium maybe plain water or water mixed
• said wind turbine rotor blades 8.30 are attached to said wind turbine rotor hub 8.20, said wind turbine rotor hub 8.20 is attached to a gas-wind turbine engine main shaft 6.50, during the operation of said gas-wind turbine engine 1.00 said wind turbine rotor blades 8.30 are pushed by the usable air flow 1.20 from the engine fan housing assembly and engine fan assembly, additionally said wind turbine rotor blades 8.30 are moved by the exhaust gas flow 4.70 which went through the gas-wind turbine engine rotor housing 2.30, said exhaust gas flow 4.70 which initially from the combustor 4.00 passes through the exhaust gas duct 4.20 of an exhaust gas duct housing 4.25 and said exhaust gas flow 4.70 moves in to said gas-wind turbine engine rotor housing 2.30 and to the vicinity of said wind turbine rotor 8.10 to push said wind turbine rotor blades 8.30 to rotate said wind turbine rotor 8.10 on the first rotation
• each of the gas-wind turbine engine rotor blades 6.60 includes second root 6.64, the second tip 6.65, second leading edge 6.66, a second trailing edge 6.67, second blade length 200, a substantially straight second line 6.63, and a second section 6.61, said second section 6.61 is generated when said gas-wind turbine engine rotor blade 6.60 is cut by a radial arc 1.70, said radial arc 1.70 cuts said gas-wind turbine engine rotor blade 6.60 between twenty and eighty percent of the gas-wind turbine engine rotor blade length 200, said second blade length 200 is the distance between the second root 6.64 and the second tip 6.65, said distance is measured along a twelfth line, said twelfth line is about perpendicular to the first rotation axis 1.10, said twelfth line intersects said second root 6.64 and intersects said second tip 6.65, in a fully assembled gas-wind turbine engine 1.00 said radial arc 1.70 having
• auxiliary air compressor 3.60 includes: an auxiliary air compressor housing, an auxiliary air compressor fan 3.63, an auxiliary air compressor fan shroud 3.64, an auxiliary air compressor first stationary vanes assembly 3.65, an auxiliary air compressor second stationary vanes assembly 3.66, an auxiliary air compressor shaft mounted vanes assembly 3.67, an auxiliary air compressor shaft 3.68, and a plurality of bearing means assembly 9.00, said auxiliary air compressor 3.60 having communicating means with an air filtering system 3.71, said air filtering system 3.71 includes at least one filtering element housing 3.73 having a filtering element 3.72, said auxiliary air compressor housing includes: an auxiliary air compressor first housing 3.61, an auxiliary air compressor second housing 3.69, auxiliary air compressor guide vanes 3.62, oil duct 7.30, air convergence zone 1.29, and an air duct 5.15, said auxiliary air compressor first stationary vanes assembly 3.65 and auxiliary air compressor second stationary vanes assembly 3.66
• a gas-wind turbine engine 1.00 according to the third disclosure wherein at least one of the fourth guide vanes 2.40 having a fourth root 2.26, a fourth segment 2.27, a fourth leading edge 2.23, a fourth trailing edge 2.24, a fourth guide vanes length 400, a substantially straight fourth line 2.22, and a fourth guide vane section 2.21, said fourth guide vane section 2.21 is generated when said fourth guide vane 2.40 is cut by a radial arc 1.70, said radial arc 1.70 cut the fourth guide vanes 2.40 between twenty percent and eighty percent the fourth guide vanes length 400, said radial arc 1.70 having center which lies about the first rotation axis 1.10 of a gas- wind turbine engine main shaft 6.50, said first guide vane length 400 is the distance between the fourth root 2.26 and the fourth segment 2.27, said distance is measured along a fourteenth line, said fourth line is about perpendicular to the first rotation axis 1.10, said fourteenth line intersects said fourth root 2.26 and said fourth segment 2.27,
• a gas-wind turbine engine 1.00 according to the third disclosure wherein each of the first guide vanes 2.50 having a first root 2.56, a first segment 2.57, a first leading edge 2.53, a first trailing edge 2.54, a first guide vanes length 100, a substantially straight first line 2.52, and a first guide vane section 2.51, said first guide vane section 2.51 is generated when said first guide vane 2.50 is cut by a radial arc 1.70, said radial arc 1.70 cut the first guide vanes 2.50 between twenty percent and eighty percent the first guide vanes length 100, said radial arc 1.70 having center which lies about the first rotation axis 1.10 of a gas-wind turbine engine main shaft 6.50, said first guide vane length 100 is the distance between the first root 2.56 and the first segment 2.57, said distance is measured along an eleventh line, said eleventh line is about perpendicular to said first rotation axis 1.10, said eleventh line intersects said first root 2.56 and said first segment 2.57 said first guide vane section 2.51

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• 2019
  • 2019-07-08 CA CA3048823A patent/CA3048823C/en active Active
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• 2020
  • 2020-04-02 EP EP20830059.0A patent/EP3853455A4/de active Pending
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